Aircraft wing assemblies

ABSTRACT

Aircraft wing assemblies are disclosed herein. An example apparatus disclosed herein includes a trailing edge of a wing of an aircraft. The trailing edge has an elastically deformable skin defining a first surface. The trailing edge has a first end to be fixed to the wing and a second end opposite the first end that is to move relative to the first end. A flap is movably coupled to the second end of the trailing edge. The flap is movable between a stowed position and a deployed position. The trailing edge is to elastically elongate when the flap moves from the stowed position to the deployed position and the trailing edge is to elastically collapse when the flap moves from the deployed position to the stowed position.

CROSS REFERENCE TO RELATED APPLICATIONS

This patent arises from a continuation of U.S. patent application Ser.No. 13/936,790, filed on Jul. 8, 2013, titled “Aircraft WingAssemblies,” which is incorporated herein by reference in its entirety.

FIELD

The present disclosure relates generally to aircraft lift systems and,more particularly, to aircraft wing assemblies.

BACKGROUND

Generally, an aircraft wing includes flaps to increase a liftcoefficient of the wing. Blown flaps employ efflux (e.g., air and/orexhaust) of engines to provide lift. The engines may be disposed aboveor beneath the wings. If the engines are disposed above the wings, theflaps are upper surface blown flaps and the efflux of the enginesinteracts with upper surfaces of the wings and the flaps to providelift. For example, the efflux may follow a curvature of the uppersurfaces of the wings and the flaps to provide lift.

SUMMARY

An example apparatus a trailing edge of a wing of an aircraft. Thetrailing edge has an elastically deformable skin defining a firstsurface. The trailing edge has a first end to be fixed to the wing and asecond end opposite the first end that is to move relative to the firstend. A flap is movably coupled to the second end of the trailing edge.The flap is movable between a stowed position and a deployed position.The trailing edge is to elastically elongate when the flap moves fromthe stowed position to the deployed position and the trailing edge is toelastically collapse when the flap moves from the deployed position tothe stowed position.

Another example apparatus includes a trailing edge of a wing of anaircraft. The trailing edge has a first end fixed to the wing and asecond end opposite the first end. The trailing edge has a flexibleupper surface and a flexible lower surface. The flexible upper surfaceand the flexible lower surface are elastically deformable to enable thesecond end to bend relative to the first end while the first end isfixed to the wing. A flap is movably coupled to the second end of thetrailing edge. The flap to cause the flexible upper surface and theflexible lower surface of the trailing edge to elastically deformbetween a first shape and a second shape different from the first shapewhen the flap moves between a first position and a second positionrelative to the trailing edge.

Another example apparatus includes a trailing edge of a wing of anaircraft. The trailing edge has an elastically deformable skin. Thetrailing edge includes a first end fixed to the wing and a second endopposite the first end to move relative to the first end. The skin is toelastically deform when the second end of the trailing edge movesrelative to the first end of the trailing edge. A flap movably coupledto the trailing edge. The flap is to apply a load to the trailing edgeto cause the skin of the trailing edge to elastically deform between afirst position and a second position when the flap moves between astowed position and a deployed position.

The features, functions and advantages that have been discussed can beachieved independently in various examples or may be combined in yetother examples further details of which can be seen with reference tothe following description and drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a front, perspective view of an example aircraft includingexample first and second wing assemblies disclosed herein.

FIG. 2 is a rear, perspective view of the example aircraft of FIG. 1.

FIG. 3 is a rear view of the example aircraft of FIGS. 1 and 2illustrating a first flap of the first wing assembly in a deployedposition.

FIG. 4 is a side view of the example aircraft of FIGS. 1-3 illustratinga second flap of the second wing assembly in the deployed position.

FIG. 5 is a rear view of the example aircraft of FIGS. 1-4 illustratingthe example first and second flaps a stowed position.

FIG. 6 is a side view of the example aircraft of FIGS. 1-5 illustratingthe example first and second flaps in the stowed position.

FIG. 7 is a schematic of an example wing assembly disclosed hereinhaving a flexible trailing edge in a first position and a flap in astowed position.

FIG. 8 is a schematic of the example wing assembly of FIG. 7illustrating the flexible trailing edge in a second position and theflap in a deployed position.

FIG. 9 is a schematic of the example wing assembly of FIGS. 7-8illustrating a range of motion of the flap between the stowed positionand deployed position.

FIG. 10 is a schematic of the example wing assembly of FIGS. 7-9illustrating the flap in the stowed position and a plot illustrating atangency discontinuity between the trailing edge and the flap.

FIG. 11 illustrates the plot of FIG. 10 and a schematic of the examplewing assembly of FIGS. 7-10 illustrating the flap in a semi-deployedposition.

FIG. 12 illustrates the plot of FIGS. 10-11 and a schematic of theexample wing assembly of FIGS. 7-11 illustrating the flap in thedeployed position.

FIG. 13 is a schematic illustrating another example wing assemblydisclosed herein having a flexible trailing edge.

FIG. 14 is a schematic illustrating the example wing assembly of FIG. 13including a flap having a first section movable relative to a secondsection.

FIG. 15 is a schematic illustrating a motion path of an aft end of aflap of another example wing assembly disclosed herein.

FIG. 16 is a schematic illustrating Fowler motion of the example flap ofFIG. 15.

FIG. 17 is a schematic illustrating the example flap of FIGS. 15-16 in adeployed position.

FIG. 18 is a schematic illustrating another example wing assemblydisclosed herein including a flap shaped to generate drag when disposedin a deployed position.

FIG. 19 is a schematic illustrating the example flap of FIG. 18 in asemi-deployed position.

FIG. 20 is a perspective view of an example trailing edge disclosedherein.

FIG. 21 is a perspective view of another example trailing edge disclosedherein including a plurality of ribs and a plurality of stringers.

FIG. 22 is a perspective view of the example trailing edge of FIG. 21including a single stringer.

FIG. 23 illustrates an example trailing edge and a plot illustrating anexample thickness profile of the trailing edge in accordance with theteachings of this disclosure.

FIG. 24 is a graph plotting the thickness and mechanical stress of theexample trailing edge of FIG. 23 over a ratio between flexure and lengthof the trailing edge.

FIG. 25 illustrates an example flap having an example track disclosedherein to enable a gap to form between a trailing edge and the flap.

FIG. 26 is a perspective, cross-sectional view of another example wingassembly disclosed herein.

FIG. 27 is a perspective view of an example track of the wing assemblyof FIG. 26.

FIG. 28 is a side, cross-sectional view of the example wing assembly ofFIGS. 26-27.

FIG. 29 is a side view of the example track of FIG. 28.

FIG. 30 is a cross-sectional view of an example roller assemblyoperatively coupled to the track of FIGS. 27-29.

The figures are not to scale. Instead, to clarify multiple layers andregions, the thickness of the layers may be enlarged in the drawings.Wherever possible, the same reference numbers will be used throughoutthe drawing(s) and accompanying written description to refer to the sameor like parts. As used in this patent, stating that any part (e.g., alayer, film, area, or plate) is in any way positioned on (e.g.,positioned on, located on, disposed on, or formed on, etc.) anotherpart, means that the referenced part is either in contact with the otherpart, or that the referenced part is above the other part with one ormore intermediate part(s) located therebetween. Stating that any part isin contact with another part means that there is no intermediate partbetween the two parts.

DESCRIPTION

Example aircraft wing assemblies disclosed herein include flaps movablycoupled to flexible trailing edges. A portion of a wing assembly thatdefines an upper surface of the wing assembly aft of a wing box and foreof at least a portion of a flap is referred to herein as “a trailingedge.” The example trailing edges disclosed herein elastically deform(e.g., bend) to enable the flaps to move through a wide range of motion.As a result, a flow turning of the example wing assemblies disclosedherein via the Coanda effect may be adjusted to enable short aircrafttake-off distances and low aircraft landing speeds. Flow turning is anability of a surface to influence fluid (e.g., air) flowing near and/orin contact with the surface to follow a curvature of a surface. TheCoanda effect is a tendency of a flowing fluid (e.g., air) near and/orin contact with a surface to follow a profile or curvature of thesurface. A turning efficiency of the surface is an angle at which thefluid turns about the surface (“a flow turning angle”) via the Coandaeffect divided by an angle through which the surface curves. The flowturning and, thus, the turning efficiency is a function of a size of aradius of curvature of the surface, a smoothness of the surface (e.g.,gaps in the surface may reduce the turning efficiency), changes of theradius of curvature of the surface over a chord (e.g., length) of thesurface, characteristics of the fluid (e.g., flow rate(s) of the fluid)and/or other factors. The turning efficiency of a flap is a function ofradius of curvature of the flap, an angle and/or distance through whichthe flap moves, and throttle settings (e.g., a flow rate of efflux) ofan aircraft and/or other factors and/or conditions. In some examples,increasing the flow turning angle of a surface decreases a turningefficiency of the surface.

An example aircraft wing assembly disclosed herein includes a flexibletrailing edge and a flap movably coupled to the trailing edge. In someexamples, the trailing edge and the flap form a substantially continuousupper blown surface (e.g., an upper surface onto which an efflux of oneor more engines is directed). The trailing edge elastically deformsduring flight when the flap applies a load to the trailing edge. In someexamples, the trailing edge is fixedly coupled to a spar of a wing box,and the trailing edge bends from a junction of the trailing edge and thespar during flight. For example, if the flap is in a retracted or stowedposition (e.g., a position in which some or all of the flap is coveredby the trailing edge), the flap may apply a force to the wing assemblythat deforms the trailing edge to decrease a camber of the trailing edge(e.g., the trailing edge may straighten). If the flap is moved from thestowed position to a deployed position, the flap may apply a load to thetrailing edge to bend the trailing edge such that a camber (e.g.,curvature) of the trailing edge and, thus, a camber of the wing assemblyincreases.

Deflection of the trailing edge facilitates a wide range of motion(e.g., rotation) of the flap as the flap moves between the stowedposition to the deployed position. As a result, adjustment of the flapenables the example wing assemblies disclosed herein to provide a lowflow turning angle and a high turning efficiency during take-off and ahigh flow turning angle and a low turning efficiency during landing withsufficient lift to enable shorter take-off distances and lower landingspeeds than aircraft employing traditional wings having rigid trailingedges. In addition, the flexible trailing edges disclosed herein enablethe example wing assemblies disclosed herein to employ smaller flapsupport assemblies (e.g., fairings, links, actuators, hinges, etc.)and/or wing boxes with larger volumes than traditional wings. Thus, theexample wing assemblies disclosed herein may be lighter than and/or havelarger fuel volume capacities than traditional wings.

FIG. 1 is front, perspective view of an example aircraft 100 disclosedherein. In the illustrated example, the aircraft 100 includes a fuselage102, a first wing assembly 104 and a second wing assembly 106. A firstengine 108 and a second engine 110 are coupled to the example first wingassembly 104. A third engine 112 and a fourth engine 114 are coupled tothe example second wing assembly 106. Other example aircraft includeother numbers (e.g., 1, 2, 3, 5, etc.) of engines.

FIG. 2 is a rear, perspective view of the example aircraft 100 ofFIG. 1. In the illustrated example, the first wing assembly 104 includesa first flap 200 movably coupled to a first flexible trailing edge 201.The example second wing assembly 106 includes a second flap 202 movablycoupled to a second flexible trailing edge 203. Although the examplefirst flap 200 and the example second flap 202 are each shown beingmonolithic, each of the first flap 200 and/or the second flap 202 maycomprise two or more flaps, which may be spaced apart spanwise along therespective wing assemblies 104, 106 and/or independently moveable (e.g.,extendible, retractable, etc.). The example first flap 200 and theexample second flap 202 of FIG. 2 are in a deployed position. When theexample first flap 200 and the example second flap 202 are in thedeployed position, cambers (e.g., curvatures) of the first wing assembly104 and the second wing assembly 106 are substantially maximized. In theillustrated example, the first wing assembly 104 and the second wingassembly 106 are mirror images but are otherwise substantially similaror the same. In other examples, the first wing assembly 104 is adifferent shape and/or size than the second wing assembly 106.

In the illustrated example, a first nozzle 204 of the first engine 108and a second nozzle 206 of the second engine 110 are disposed above thefirst wing assembly 104 in the orientation of FIG. 2. The first nozzle204 and the second nozzle 206 direct efflux (e.g., air and/or exhaust)of the first engine 108 and the second engine 110, respectively, ontoand/or along a first upper surface 208 of the first wing assembly 104.As the efflux flows along the first upper surface 208, the effluxfollows a curvature of the first upper surface 208 and, thus, flowsdownward. As a result, the efflux generates lift. A phenomenon in whichthe efflux follows the curvature of the first wing assembly 104 and/orthe second wing assembly 106 is referred to herein as “the CoandaEffect.”

In the illustrated example, a third nozzle 210 of the third engine 112and a fourth nozzle 212 of the fourth engine 114 are disposed above thesecond wing assembly 106 in the orientation of FIG. 2. The third nozzle210 and the fourth nozzle 212 direct efflux of the third engine 112 andthe fourth engine 114, respectively, onto and/or along a second uppersurface 214 of the second wing assembly 106. As the efflux flows alongthe second upper surface 214, the efflux follows a curvature of thesecond upper surface 214 and, thus flows downward. As a result, theefflux of the third engine 112 and the fourth engine 114 generates lift.

FIG. 3 is a rear view of the example first wing assembly 104 of theaircraft of FIGS. 1-2. In the illustrated example, the first flap 200includes a plurality of tracks 300 defining a motion path of the firstflap 200 relative to the first trailing edge 201. In the illustratedexample, the tracks 300 are curved. In other examples, the tracks 300are other shapes. In the illustrated example, the tracks 300 are spacedapart spanwise along the first flap 200. The second flap 202 of theexample second wing assembly 106 includes tracks that are mirror imagesof the tracks 300 but are otherwise substantially similar or identicalto the example tracks 300 of FIG. 3.

In some examples, the first trailing edge 201 and the second trailingedge 203 elastically deform under loads applied by the first flap 200and the second flap 202, respectively. In the illustrated example, theloads applied by the first flap 200 and the second flap 202 change(e.g., increase or decrease) as the example first flap 200 and theexample second flap 202 move relative to the first trailing edge 201 andthe second trailing edge 203 (e.g., via the tracks 300). As a result,the first trailing edge 201 and the second trailing edge 203 bend orflex when the first flap 200 and the second flap 202, respectively,extend or retract. In some examples, the loads applied by the first flap200 and the second flap 202 to the first trailing edge 201 and thesecond trailing edge 203 are affected and/or influenced by air flowingaround the first flap 200 and the second flap 202, respectively.

FIG. 4 is a side view of the example aircraft 100 of FIGS. 1-3illustrating the second flap 202 in the deployed position. In someexamples, the first flap 200 and the second flap 202 are moved to thedeployed position before and/or during landing (e.g., landing approach,touchdown, and/or rollout). In the illustrated example, the second wingassembly 106 includes a flap support assembly 400. The example flapsupport assembly 400 includes a plurality of fairings 402, 404, 406,408. In some examples, the flap support assembly 400 includes one ormore actuators to move the second flap 202 between a retracted or stowedposition and the deployed position. The example first wing assembly 104includes a flap support assembly substantially similar or identical tothe flap support assembly 400 of FIG. 4.

FIGS. 5-6 illustrate the example aircraft of FIGS. 1-4 in which thefirst flap 200 and the second flap 202 are in the stowed position. Insome examples, the first flap 200 and/or the second flap 202 are in thestowed position during a cruising phase of flight in which the exampleaircraft 100 is flying at a substantially constant or level altitudeand/or airspeed. In some examples, when the first flap 200 and/or thesecond flap 202 are in the stowed position, portions of the first flap200 and the second flap 202 are covered by (e.g., retracted into and/orbeneath) the first trailing edge 201 and the second trailing edge 203,respectively, to reduce and/or minimize the cambers and/or surface areasof the first wing assembly 104 and the second wing assembly 106.

FIG. 7 is a schematic, cross-sectional view of an example wing assembly700 disclosed herein, which may be used to implement the example firstwing assembly 104 and/or the example second wing assembly 106 of FIGS.1-6. The example wing assembly 700 of FIG. 7 includes a wing box 702.The example wing box 702 includes an upper skin 704, a lower skin 706, afirst (e.g., front) spar 708 and a second (e.g., rear) spar 710. In theillustrated example, the upper skin 704 is coupled to the lower skin 706fore of the first spar 708 to form a leading edge 712 of the wingassembly 700.

The example wing assembly 700 also includes a trailing edge 714 and aflap 716. In the illustrated example, the trailing edge 714 is fixedlycoupled to the second spar 710. In the illustrated example, the flap 716is in a stowed position in which a first section 718 of the flap 716 iscovered by the trailing edge 714 and a second section 720 of the flap716 extends aft of the trailing edge 714. In some examples, when theflap 716 is in the stowed position, the first section 718 and the secondsection 720 of the flap 716 are covered by the trailing edge 714. Insome examples, the flap 716 is in the stowed position during a cruisingstage of flight to reduce and/or minimize a surface area of the wingassembly 700.

In the illustrated example, the trailing edge 714 is in a firstposition. When the trailing edge 714 is in the first position, thetrailing edge 714 has a first shape (e.g., curvature). As described ingreater detail below, when the flap 716 moves from the stowed positionto a deployed position (FIG. 8), the trailing edge 714 elasticallydeforms (e.g., bends or deflects) to a second position and has a secondshape.

In the illustrated example, the upper skin 704, the trailing edge 714and the flap 716 of the example wing assembly 700 of FIG. 7 form asubstantially continuous upper blown surface 722 (e.g., a surface withsubstantially no gaps). In the illustrated example, the upper skin 704and the trailing edge 714 meet (e.g., couple, join and/or abut) at afirst juncture 726 at and/or along the second spar 710. In someexamples, a first surface 728 of the upper skin 704 has a same slope asa second surface 730 of the trailing edge 714 at the first juncture 726(e.g., a tangency continuity is present between the first surface 728and the second surface 730 at the first juncture 726).

In the illustrated example, the flap 716 includes a third surface 732(e.g., an upper surface) that meets the second surface 730 of thetrailing edge 714 at a second juncture 734. Thus, when the example flap716 is in the stowed position, the third surface 732 along the secondsection 720 of the flap 716 forms a portion of the example upper blownsurface 722 of FIG. 7. In the illustrated example, the second surface730 and the third surface 732 have substantially a same slope at thesecond juncture 734 (e.g., a tangency continuity is present between thesecond surface 730 and the third surface 732 at the second juncture734).

The example flap is movable between the stowed position and the deployedposition (FIG. 8). In the illustrated example, the flap 716 is rotatablycoupled to a flap support (e.g., a link or brace covered by a fairing735) via a first link 736 and a second link 738. The example flapsupport, the first link 736 and the example second link 738 areoperatively coupled to a hinge 740. An actuator 742 is operativelycoupled to the first link 736 to rotate the flap 716 about the hinge740. Thus, the example hinge 740 defines an axis of rotation of the flap716 of FIG. 7, and the example flap 716 is movable in a substantiallycircular path about the hinge 740. In other examples, the flap 716 ismovable in a non-circular path relative to the wing box 702. In theillustrated example, the actuator 742 is coupled to a third link 744.The example third link 744 is coupled to the wing box 702 and the flapsupport covered by the fairing 735. In other examples, the flap 716 ismovably coupled to the wing box 702 via a track, a four bar linkage, asix bar linkage, a multi-bar link, and/or any other mechanism(s).

FIG. 8 is a schematic, cross-sectional view of the example wing assembly700 of FIG. 7 illustrating the example flap 716 in the deployedposition. The example flap 716 of FIG. 8 is movably coupled to thetrailing edge 714 to enable the flap 716 to move relative to thetrailing edge 714 as the flap 716 rotates about the hinge 740. In theillustrated example, the flap 716 includes a track 800. The exampletrack 800 of FIG. 8 is disposed on and/or coupled to a side 801 of theflap 716. In some examples, the flap 716 defines a channel, and thetrack 800 is disposed in the channel. In some examples (e.g., theexamples of FIGS. 26-30 disclosed below), the track 800 is disposed onand/or coupled to the third surface 732 of the flap 716. A rollerassembly 802 (e.g., one or more wheels) is disposed in the track 800 andcoupled to the trailing edge 714. Thus, the example roller assembly 802operatively couples the trailing edge 714 to the flap 716. In otherexamples, the trailing edge 714 includes a slider (e.g., an arm orprotrusion fixedly coupled to the trailing edge 714) disposed in thetrack 800 to slidably couple the flap 716 to the trailing edge 714. Insome example, the slider and/or the track 800 include lubricant(s)and/or low-friction materials such as, for example, plastic tofacilitate movement of the slider along the track 800.

When the example actuator 742 actuates, the actuator 742 rotates theflap 716 about the hinge 740. As the flap 716 rotates about the hinge740, the flap 716 moves fore or aft relative to the trailing edge 714about a motion path defined by the track 800. When the example flap 716is in the deployed position, a camber of the example wing assembly 700is maximized.

In the illustrated example, a position and/or movement of the flap 716affects a load applied by the flap 716 to the trailing edge 714. In theillustrated example, the track 800 is curved. A first radius ofcurvature of the example track 800 is greater than a turning radius ofthe flap 716 about the hinge 740. In other examples, the first radius ofcurvature of the track 800 is less than or the same as the turningradius of the flap 716 about the hinge 740. The example track 800 curvesand/or extends away from (e.g., not along) a circular path of the flap716 about the hinge 740. Thus, the track 800 is not concentric to thecircular path of the flap 716. As a result, the track 800 and the rollerassembly 802 function as a cam and a follower, respectively, as the flap716 rotates about the hinge 740. For example, as the flap 716 moves fromthe stowed position illustrated in FIG. 7 to the deployed positionillustrated in FIG. 8, the flap 716 pulls downward on the trailing edge714 in the orientation of FIG. 8. In the illustrated example, the flap716 applies a maximum load to the trailing edge 714 when the flap 716 isin the stowed position and/or the deployed position.

In the illustrated example, the trailing edge 714 is flexible orelastically deformable. As a result, the trailing edge 714 elasticallydeforms (e.g., bends) under the load applied to the trailing edge 714 bythe flap 716. In some examples, when the trailing edge 714 is in thesecond position (e.g., when the flap 716 is in the deployed position),the trailing edge has a second shape (e.g., curvature) different thanthe first shape of the trailing edge 714 in the first position (e.g.,when the flap 716 is in the stowed position). In some examples, thesecond shape has a smaller radius of curvature than the first shape. Insome examples, a change in curvature of the trailing edge 714 issubstantially uniform along a chord (e.g., a length from the firstjuncture 726 to the second juncture 734) of the trailing edge 714 whenthe trailing edge 714 deflects (e.g., elastically deforms) from thefirst shape to the second shape. In the illustrated example, when theexample flap 716 is in the deployed position, a curvature of the upperblown surface 722 has a substantially constant radius. In some examples,a second actuator is operatively coupled to the trailing edge 714 toapply a load to the trailing edge 714 to elastically deform the trailingedge 714. In some examples, the second actuator cooperates with the flap716 to elastically deform the trailing edge 714. In other examples, theflap 716 does not apply a load to the trailing edge 714, and the secondactuator controls an amount of elastic deformation of the trailing edge714.

FIG. 9 is a schematic of the example wing assembly 700 of FIGS. 7-8illustrating a range of motion of the example flap 716. Deflection orflexure of the trailing edge 714 enables the example flap 716 to movethrough a greater range of motion than upper blown flaps of traditionalwings with rigid or inflexible trailing edges. For example, thedeflection of the trailing edge 714 from the first position to thesecond position facilitates rotation of the flap 716 and, thus,adjustment of the camber of the upper blown surface 722. In theillustrated example, a chord line 900 of the wing assembly 700 issubstantially horizontal in the orientation of FIG. 9. In otherexamples, the chord line 900 is not horizontal. The chord line 900 is aline extending from the leading edge 712 of the example wing assembly700 to a tip 902 of the flap 716 when the flap 716 is in the stowedposition. When the example flap 716 is in the stowed position, thetrailing edge 714 is disposed above the chord line 900 in theorientation of FIG. 9. In other examples, the trailing edge 714 is inother locations relative to the chord line 900 when the flap 716 is inthe stowed position.

In the illustrated example, the deflection of the trailing edge 714enables the flap 716 of FIG. 9 to rotate 69.9 degrees about the hinge740 when the flap 716 moves from the stowed position to the deployedposition. However, the above-noted angle is merely an example and, thus,other angles of rotation may be used without departing from the scope ofthis disclosure. When the flap 716 is in the deployed position, the flap716 and a portion of the trailing edge 714 are disposed below the chordline 900 in the orientation of FIG. 9. In addition, the tip 902 of theexample flap 716 is farther from the chord line 900 than the hinge 740and a center of curvature 904 of the upper blown surface 722. In otherexamples, the tip 902 of the flap 716 is in other locations relative tothe chord line 900, the hinge 740 and/or the center of curvature 904when the flap 716 is in the deployed position.

The deflection of the trailing edge 714 also enables a turning radius906 of the flap 716 to be smaller than a radius of curvature 908 of theupper blown surface 722. As a result, the example wing assembly 700employs a smaller and/or simplified flap support assembly (e.g., thefairing 735, the first link 736, the second link 738, the third link744, the fourth link, the actuator 742) and/or a larger wing box (e.g.,the wing box 702) than traditional wings having rigid trailing edges. Inthe illustrated example, the turning radius 906 is a radius about whichthe flap 716 rotates via the hinge 740. The example flap 716 of FIG. 7moves in a substantially circular path. Thus, the example turning radius906 of FIG. 9 is substantially constant. In other examples (e.g., theexamples illustrated in FIGS. 16-17), the flap 716 moves in anon-circular path and, thus, the turning radius 906 is not constant. Forexample, the turning radius 906 may increase, decrease, vary, etc. asthe flap 716 moves between the stowed position and the deployedposition. In some examples, the flap 716 moves linearly (e.g.,translates) and/or rotates as the flap 716 moves between the stowedposition and deployed position.

The radius of curvature 908 of the upper blown surface 722 is a radiusextending from the center of curvature 904 of the upper blown surface722 to the upper blown surface 722. Because the turning radius 906 ofthe flap 716 is less than the radius of curvature 908 of the upper blownsurface 722, the axis of rotation of the flap 716 and, thus, the hinge740 may be disposed closer to the chord line 900 than the center ofcurvature 904 of the upper blown surface 722. In the illustratedexample, the hinge 740 is a first distance from the chord line 900corresponding 17.2 percent of a length of the chord line 900. Theexample center of curvature 904 of the upper blown surface 722 when theflap 716 is in the deployed position is a second distance from the chordline 900 corresponding to 34.7 percent of the length of the chord line900. In the illustrated example, the radius of curvature 908 of theupper blown surface 722 when the flap 716 is in the deployed positionhas a substantially constant length corresponding to 38.6 percent of thelength of the chord line 900.

The deflection of the trailing edge 714 also enables the upper blownsurface 722 to be substantially continuous as the flap 716 movesrelative to the trailing edge 714. For example, the trailing edge 714bends with movement of the flap 716, thereby maintaining or preservingthe second junction 734 as the flap 716 moves between the stowedposition and the deployed position. In the illustrated example, thetrailing edge 714 also bends to enable a radius of curvature of thesecond surface 730 to be substantially similar or identical to a radiusof curvature of the third surface 732. Thus, although the turning radius906 of the flap 716 is less than the radius of curvature 908 of theupper blown surface 722, the deflection of the trailing edge 714 enablesthe radius of curvature 908 of the upper blown surface 722 along thetrailing edge 714 and the flap 716 to be substantially constant.

FIGS. 10-12 are schematics of the example wing assembly 700 of FIGS. 7-9including a plot 1000 of a difference between a first slope of thesecond surface 730 of the trailing edge 714 and a second slope of thethird surface 732 of the flap 716 at the second juncture 734 as the flap716 moves from the stowed position (FIG. 10) to the deployed position(FIG. 12). Referring to FIG. 10, when the example flap 716 is in thestowed position, the second surface 730 and the third surface 732 havesubstantially the same slope at the second juncture 734. Referring toFIG. 11, as the flap 716 moves from the stowed position toward thedeployed position, and the second slope changes relative to the firstslope at the second juncture 734. As a result, a tangency discontinuitybetween the second surface 730 and the third surface 732 (e.g., adifference between the first slope and the second slope) is present atthe second juncture 734 when the example flap 716 is in a positionbetween the stowed position and the deployed position. In theillustrated example, a maximum tangency discontinuity between the secondsurface 730 and the third surface 732 is 7.8 degrees when the exampleflap 716 is in a position 49.2 percent through the example motion pathdefined by the track 800 relative to the stowed position. In someexamples, the maximum tangency discontinuity is present at otherpositions along the track 800. Other examples have other maximumtangency discontinuities and/or substantially no tangency discontinuity.When the tangency discontinuity exists between the second surface 730and the third surface 732, a portion of the upper blown surface 722forms a concavity 1100 at or near the second juncture 734. Referring toFIG. 12, when the example flap 716 is in the deployed position, thefirst slope and the second slope are substantially the same. In someexamples, the portion of the upper blown surface 722 forms a convexityat or near the second juncture 734 when the flap 716 is in the stowedposition and/or the deployed position. In some examples, no tangencydiscontinuities are present when the flap 716 is in one or morepositions between the stowed position and the deployed position (e.g.,when the flap 716 is approximately 25 percent through the example motionpath defined by the track 800).

In some examples, the trailing edge 714 includes a second rollerassembly disposed in the track 800 of the flap 716 to substantiallyprevent the tangency discontinuity between the second surface 730 andthe third surface 732 at the second juncture 734 as the flap 716 movesbetween the stowed position and the deployed position.

FIG. 13 is a schematic of another example wing assembly 1300 disclosedherein. In the illustrated example, the wing assembly 1300 includes aflexible trailing edge 1302 fixedly coupled to a wing box 1304. A flap1306 is movably coupled to the trailing edge 1302 to enable the flap1306 to move from a stowed position to a deployed position. The exampleflap 1306 of FIG. 13 rotates about a pivot 1308 (e.g., a hinge) via afirst flap support assembly (not shown) (e.g., a fairing, one or morelinks, an actuator, and/or any other components). In the illustratedexample, the flap 1306 rotates about the pivot 1308 via a substantiallyconstant turning radius 1310. When the flap 1306 rotates about the pivot1308, the flap 1306 applies a force to the trailing edge 1302. As aresult, the trailing edge 1302 elastically deforms (e.g., bends). In theillustrated example, the flap 1306 and the trailing edge 1302 form asubstantially continuous upper blown surface 1312. In the illustratedexample, the upper blown surface 1312 has a substantially constantradius of curvature 1314.

In the illustrated example, the flap 1306 is in the deployed position.When the example flap 1306 moves from the stowed position to thedeployed position, a chord of the wing assembly 1300 (e.g., a distancebetween a leading edge 1316 of the wing assembly 1300 and a rear tip1318 of the flap 1306) increases from a first length to a second length.Motion of the example flap 1306 that increases the length of the chordis referred herein as “Fowler motion.” In the illustrated example, thesecond length is a length of 105.1 percent of the first length. In otherexamples, the second length is other lengths. When the example flap 1306is in the deployed position, the rear tip 1318 of the flap 1306 is abouta same distance from a chord line 1320 of the wing assembly 1300 as thepivot 1308. In the illustrated example, the pivot 1308 and the rear tip1318 of the flap 1306 are a distance of 14.4 percent of the first lengthfrom the chord line 1320. However, the above-noted dimension is merelyan example and, thus, other dimensions may be used without departingfrom the scope of this disclosure.

FIG. 14 illustrates the example wing assembly 1300 of FIG. 13 in whichthe flap 1306 has a first section 1400 movably coupled a second section1402. The example first section 1400 is aft of the second section 1402and moves (e.g., telescopes) relative to the second section 1402 toincrease or decrease, respectively, a camber and/or a chord of the flap1306 and, thus, the upper blown surface 1312.

FIG. 15 illustrates another example wing assembly 1500 disclosed hereinhaving a flexible trailing edge 1502 and a flap 1504 movably coupled tothe flexible trailing edge 1502. In the illustrated example of FIG. 15,the flap 1504 is in a stowed position. The example flap 1504 is movablein a non-circular first motion path 1506 between the stowed position, asemi-deployed position (FIG. 16) and a deployed position (FIG. 17). Insome examples, the flap 1504 is movable along the first motion path 1506via a one or more actuators coupled to a multi-bar link and/or any otherflap support assembly.

FIG. 16 illustrates the example flap 1504 of FIG. 15 in thesemi-deployed position. In the illustrated example, the flap 1504 movesaft from the stowed position to the semi-deployed position substantiallywithout deflection (e.g., bending) of the trailing edge 1502. As aresult, the first motion path 1506 provides Fowler motion of the flap1504 when the example flap 1504 moves from the stowed position to thesemi-deployed position. In some examples, the flap 1504 is positioned inthe semi-deployed position during take-off.

FIG. 17 illustrates the example flap 1504 of FIGS. 15-16 in the deployedposition. As the example flap 1504 moves from the semi-deployed positionto the deployed position, the example trailing edge 1502 deflectsdownward in the orientation of FIG. 17 along second motion path 1700.Deflection of the example trailing edge 1502 facilitates movement of theflap 1504 that increases a camber of the wing assembly 1500 and enablesan upper surface 1702 of the wing assembly 1500 to be substantiallycontinuous as the example flap 1504 moves along the first motion path1506. In the illustrated example, a fore end 1704 of the trailing edge1502 is fixedly coupled to a spar 1706 of the example wing assembly1500.

FIG. 18 illustrates another example wing assembly 1800 in accordancewith the teachings of this disclosure. The example wing assembly 1800includes a flexible trailing edge 1802 and a flap 1804 movably coupledto the flexible trailing edge 1802. In the illustrated example, the flap1804 is in a deployed position. The example flap 1804 defines an upperblown surface 1806 having a first section 1808, a second section 1810and a third section 1812. In the illustrated example, the first section1808 has a first radius of curvature and the second section 1810 has asecond radius of curvature. The example second radius of curvature isless than the first radius of curvature and forms a swell or convexity.In some examples, the third section 1812 has a third radius of curvaturesubstantially equal to and/or greater than the first radius ofcurvature. As efflux from an engine and/or air flow along the upperblown surface 1806, a change of slope between the first section 1808,the second section 1810 and/or the third section 1812 of the upper blownsurface 1806 causes and/or directs the efflux and/or the air to separatefrom the flap 1804 (e.g., flow away from the upper blown surface 1806),thereby producing drag. During landing, the drag produced via the secondsection 1810 of the upper blown surface 1806 enables high thrust levelsto be employed without undesirably increasing a landing speed of anaircraft descending at a given glide slope on which the example wingassembly 1800 is employed.

FIG. 19 illustrates the example wing assembly 1800 of FIG. 18 in whichthe example flap 1804 is in a semi-deployed position. In some examples,the flap 1804 is positioned in the semi-deployed position duringtake-off. In the illustrated example, when the flap 1804 is positionedin the semi-deployed position, the first section 1808 and the secondsection 1810 of the upper blown surface 1806 of the flap 1804 arecovered by the example trailing edge 1802. As a result, the examplesecond section 1810 produces less or substantially no drag when theexample flap 1804 is in the semi-deployed position and/or when theexample second section 1810 is fore of the semi-deployed position (e.g.,in a stowed position). In the illustrated example, second section 1810is disposed adjacent an aft end 1900 of the trailing edge 1802. Theexample third section 1812 of the flap 1804 is aft of the trailing edge1802.

FIG. 20 is a perspective, cutaway view illustrating a portion of anexample trailing edge 2000 disclosed herein, which may be used toimplement the example first trailing edge 201 of FIGS. 1-6, the examplesecond trailing edge 203 of FIGS. 1-6, the example trailing edge 714 ofFIGS. 7-12, the example trailing edge 1302 of FIGS. 13-14, the exampletrailing edge 1502 of FIGS. 16-17, the example trailing edge of FIGS.18-19 and/or any other trailing edge. Other portions of the trailingedge 2000 along a span of the trailing edge 2000 are not shown. A firstend 2002 of the example trailing edge 2000 is to be coupled to a wingbox (e.g., cantilevered from a spar, etc.). In some examples, the firstend 2002 includes mechanical fasteners, brackets, couplings and/or otherdevices to couple the trailing edge 2000 to the wing box. A second end2004 of the example trailing edge 2000 is to abut or juxtapose a flap(e.g., the example first flap 200 of FIGS. 1-6, the example second flap202 of FIGS. 1-6, the example flap 716 of FIGS. 7-12, the example flap1306 of FIGS. 13-14, the example flap 1504 of FIGS. 15-17, the exampleflap 1804 of FIGS. 18-19 and/or any other flexible flap). The exampletrailing edge 2000 may have any spanwise shape. For example, thetrailing edge 2000 may be tapered or twisted along a span of thetrailing edge 2000.

In the illustrated example, the trailing edge 2000 includes a flexibleskin 2006 defining an upper surface 2008. The example trailing edge 2000includes a roller assembly 2010. The example roller assembly 2010 is tobe operatively coupled to the flap via a track (e.g., the example track800 of FIG. 8) to enable the flap to move relative to the trailing edge2000. In the illustrated example, the roller assembly 2010 includes afirst wheel 2012, a second wheel 2014 and a third wheel 2016. Otherexamples include other numbers of roller assemblies (e.g., 2, 3, etc.)and/or other numbers of wheels (e.g., 1, 2, 4, 5, etc.). The examplewheels 2012, 2014, 2016 are spaced apart spanwise along the trailingedge 2000 and are coupled to the skin 2006 via brackets or struts 2018,2020, 2022. In the illustrated example, a spanwise brace or stringer2024 is coupled to the skin 2006 and the struts 2018, 2020, 2022 tosupport a portion of a load applied to the trailing edge 2000 by theflap. Some examples do not include the stringer 2024.

In other examples, the trailing edge 2000 includes a slider (e.g., oneor more protrusions fixedly coupled to the trailing edge 2000) disposedin the track to slidably couple the flap to the trailing edge 2000. Insome example, the slider and/or the track include lubricant(s) and/orlow-friction materials such as, for example, plastic to facilitatemovement of the slider along the track.

In the illustrated example, the roller assembly 2010 is disposedadjacent the second end 2004 to enable the flap to apply a force or loadto the example skin 2006 to elastically deform (e.g., bend) the skin2006 when the flap moves relative to the trailing edge 2000. In theillustrated example, a thickness of the example skin 2006 decreases fromthe first end 2002 to the second end 2004. A thickness of the skin 2006along a span of the skin 2006 is substantially constant in theillustrated example. In other examples, the thickness of the skin 2006along the span of the skin 2006 is not substantially constant (e.g., thethickness decreases along the span of the skin 2006).

FIG. 21 illustrates another example trailing edge 2100 including a skin2102 supported by a plurality of stringers 2104 and a plurality offlexible ribs 2106. In the illustrated example, the ribs 2106 are spacedapart spanwise along the example trailing edge 2100. The example ribs2106 extend from a fore end 2108 of the skin 2102 to a roller assembly2110 coupled to the skin 2102 adjacent an aft end 2112 of the skin 2102.In the illustrated example, the roller assembly 2110 is coupled to theskin 2102 via the ribs 2106. The stingers 2104 of the illustratedexample extend spanwise along the skin 2102 and are spaced apart betweenthe fore end 2108 of the skin 2102 and the roller assembly 2110.

In the illustrated example, a flap is to be movably coupled to thetrailing edge 2100 via the roller assembly 2110. In other examples, thetrailing edge 2100 includes a slider (e.g., one or more protrusionsfixedly coupled to the trailing edge 2100) disposed in the track toslidably couple the flap to the trailing edge 2100.

When the flap moves relative to the example trailing edge 2100, the flapapplies a load to the skin 2102 via the roller assembly 2110, the ribs2106 and/or the stringers 2104. In the illustrated example, the load istransferred from the roller assembly 2110 to the skin 2102 directly bythe example ribs 2106 and indirectly by the example stringers 2104. Inthe illustrated example, thicknesses of the ribs 2106 decrease alonglengths (e.g., from the fore end 2108 toward the aft end 2112 of thetrailing edge 2100) of the ribs 2106. As a result, the example ribs 2106and, thus, the skin 2102 bend under the load of the flap. In theillustrated example, a thickness of the skin 2102 is substantiallyconstant. In other examples, the thickness of the skin 2102 may not besubstantially constant (e.g., the thickness may vary, the thickness mayincrease or decrease in a spanwise direction, the thickness may increaseor decrease from the fore end 2108 to the aft end 2112 of the skin 2102,etc.).

FIG. 22 illustrates the example trailing edge 2100 of FIG. 21 having asingle stringer 2104 coupled to the skin 2102 and the roller assembly2110. In some examples, two or more stringers are coupled togetherand/or to the skin 2102 to form the example stringer 2104 of FIG. 22. Inthe illustrated example, a portion of the load applied to the ribs 2106is directly transferred to the skin 2102 to facilitate bending of theexample trailing edge 2100.

FIG. 23 is a schematic of an example trailing edge 2300 and a plot 2302illustrating a thickness profile of the trailing edge 2300 in accordancewith the teachings of this disclosure. In the illustrated example, athickness of the trailing edge 2300 decreases from a fore end 2304 to anaft end 2306 of the trailing edge 2300 to enable the trailing edge 2300to flex or bend under the influence of mechanical stress (e.g., when aload is applied to the trailing edge 2300 via a flap and/or air duringflight). In the illustrated example, when the trailing edge 2300 isunder substantially no mechanical stress, the trailing edge 2300 is in afirst position, which is indicated by line 2308. When the exampletrailing edge 2300 is in the first position, the trailing edge 2300 hasa first curvature. In some examples, the trailing edge 2300 is undersubstantially no mechanical stress when the flap is in a semi-deployedposition.

When the flap is in a stowed position during flight, an upward force inthe orientation of FIG. 23 is applied to the trailing edge 2300 via theflap. As a result, the trailing edge 2300 is bent (e.g., straightened)from the first position to a second position. The example trailing edge2300 is shown in the second position in FIG. 23. When the exampletrailing edge 2300 is in the second position, the trailing edge 2300 hasa second curvature. The second curvature has a greater radius ofcurvature than the first curvature. When the flap is moved to a deployedposition, the flap applies a load to the trailing edge 2300 to bend thetrailing edge 2300 to a third position, which is indicated by line 2310.When the trailing edge 2300 is in the third position, the trailing edge2300 has a third curvature. In the illustrated example, the thirdcurvature has a smaller radius of curvature than the first curvature andthe second curvature. In some examples, the first curvature, the secondcurvature and/or the third curvature is substantially circular. In otherexamples, the first curvature, the second curvature and/or the thirdcurvature is non-circular.

In the illustrated example, a first amount of deflection of the trailingedge 2300 from the first position (line 2308) to the second position (asshown in FIG. 23) is substantially the same as a second amount ofdeflection of the trailing edge 2300 from the first position to thethird position (line 2310). As a result, an amount of mechanical stressexperienced by the example trailing edge 2300 in the second position issubstantially the same as the amount of mechanical stress experienced bythe trailing edge 2300 in the third position. In other examples, thefirst amount of deflection and the second amount of deflection aredifferent.

In the illustrated example, a change in curvature of the exampletrailing edge 2300 is substantially uniform over a length of thetrailing edge 2300 (e.g., from the fore end 2304 to the aft end 2306) asthe trailing edge 2300 deflects between the second position and thethird position. To enable the change in the curvature to besubstantially uniform, cross-sectional dimensions and materialproperties of the example trailing edge 2300 provide a bending rigidityof the trailing edge 2300 at a midpoint of the length of the trailingedge 2300 that is about half of a bending rigidity of the trailing edge2300 at the fore end 2304. Other examples have dimensions (e.g.,thicknesses) and/or materials that enable the trailing edge 2300 to havevarying or different changes in curvature along the length of thetrailing edge 2300 as the trailing edge 2300 bends. In some examples,the trailing edge 2300 includes one or more material layers to enablethe trailing edge 2300 to deflect between the second position and thethird position to in a desired shape.

FIG. 24 is a graph 2400 plotting thickness and mechanical stress of theexample trailing edge 2300 of FIG. 23 over a ratio between flexure andthe length of the trailing edge 2300. In the illustrated example, thetrailing edge 2300 is modeled as a beam to calculate the mechanicalstress. In the illustrated example, a thickness of the trailing edge2300 at the fore end 2304 is approximately 0.5 inches and a modulus ofelasticity of a material composing the trailing edge 2300 isapproximately 2,000 KSI. However, the above-noted dimension and materialproperty are merely examples and, thus, other dimensions and/ormaterials having other material properties may be used without departingfrom the scope of this disclosure. In the illustrated example, thethickness of the trailing edge 2300 decreases non-linearly over thelength of the trailing edge 2300.

FIG. 25 is a schematic of an example flap 2500 and an example flexibletrailing edge 2502 disclosed herein. In the illustrated example, theflap 2500 is movably coupled to the trailing edge 2502. The example flap2500 includes a track 2504, and the trailing edge 2502 includes a rollerassembly 2506 disposed in the track 2504. The example track 2504 definesa motion path of the flap 2500 relative to the trailing edge 2502.

In some examples, the flap 2500 defines the example track 2504. In someexamples, the flap 2500 defines a channel or slot, and the track 2504 isreceived in the slot and coupled to the flap 2500. In some examples, thetrack 2504 has a hooked and/or T-shaped cross-sectional shape to enablethe track 2504 to engage the roller assembly 2506. In some examples, thetrack 2504 is disposed in the slot to be recessed from a surface (e.g.,an upper surface) of the flap 2500. In some examples, a portion of thetrack 2504 extends out of the slot. In some examples, the flap 2500 doesnot include the channel or slot and the track 2504 is coupled to thesurface.

In the illustrated example, the track 2504 includes a first section2508, a second section 2510 and a third section 2512. When the exampleflap 2500 is positioned relative to the trailing edge 2502 such that theroller assembly 2506 is disposed in the first section 2508 or the thirdsection 2512 of the track 2504, a first upper surface 2514 of the flap2500 and a second upper surface 2516 of the trailing edge 2502 form asubstantially continuous upper blown surface.

In the illustrated example, the second section 2510 of the track 2504 iscurved such that the second section 2510 extends from the first section2508 toward the first upper surface 2514 of the flap 2500 and thenextends away from the first upper surface 2514 to the third section2512. As a result, when the example flap 2500 is positioned relative tothe trailing edge 2502 such that the roller assembly 2506 is disposed inthe second section 2510 of the track 2504, the first surface 2514 andthe second surface 2516 are non-continuous. For example, the secondsection 2510 of the track 2504 guides the flap 2500 away from the secondsurface 2516 of the trailing edge 2502 to form a space or gap 2518between the trailing edge 2502 and the flap 2500. The example gap 2518enables air flowing beneath the trailing edge 2502 to flow through thegap 2518 and over the first surface 2514 of the flap 2500. The air frombeneath the trailing edge 2510 energizes air over the first surface 2514and produces lift as the air follows a curvature of the first surface2514.

In other examples, the gap 2518 is formed by extending a length of theroller assembly 2506. For example, the roller assembly 2506 may includean actuator to extend or retract the roller assembly 2506 relative tothe trailing edge 2502 to form the gap 2518. In some examples, theroller assembly 2506 includes an extendible link coupled via one or moreexplosive bolts. If the explosive bolts are activated, the boltsdecouple from the link to enable the link to extend, thereby forming thegap 2518.

FIG. 26 is a perspective, cross-sectional view of another example wingassembly 2600 disclosed herein. Aspects of the example wing assembly2600 may be used to implement the example first wing assembly 104 ofFIGS. 1-6, the example second wing assembly 106 of FIGS. 1-6, theexample wing assembly 700 of FIGS. 7-12, the example wing assembly 1300of FIGS. 13-14, the example wing assembly 1500 of FIGS. 15-17, theexample wing assembly 1800 of FIGS. 18-19, and/or another example wingassembly. In the illustrated example, the wing assembly 2600 includes awing box 2602 having a first upper surface 2604, a flexible trailingedge 2606 including a second upper surface 2608, and a flap 2610including a third upper surface 2612. In the illustrated example, thefirst upper surface 2604, the second upper surface 2608 and the thirdupper surface 2612 form a substantially continuous upper blown surface.The example flap 2610 is movably coupled to the trailing edge 2606 viafive tracks 2614 a-2614 e. In other examples, the wing assembly 2600includes other numbers of tracks (e.g., 1, 2, 4, 6, 7, 10, etc.). Theexample tracks 2614 a-2614 e define a motion path of the flap 2610relative to the trailing edge 2606. In the illustrated example, the flap2610 is in a stowed position.

FIG. 27 is a perspective view of one of the example tracks 2614 a-2614 eof FIG. 26. In the illustrated example, the track 2614 a is coupled tothe third upper surface 2612 of the flap 2610. The example track 2614 aextends from the third upper surface 2612 through a slot 2700 of thetrailing edge 2606. A roller assembly 2702 is coupled to the secondupper surface 2608 of the trailing edge 2606. The example rollerassembly 2702 has a first roller 2704 and a second roller 2706. In otherexamples, the roller assembly 2702 includes other numbers of rollers(e.g., 1, 3, 4, 5, etc.). The first roller 2704 is coupled to a firstside 2708 of the track 2614 a, and the second roller 2706 is coupled toa second side 2710 of the track 2614 a. In the illustrated example, thetrack 2614 a has a T-shaped cross-section. In other examples, the track2614 a has other cross-sectional shapes such as, for example, anI-shaped cross-section.

FIGS. 28-29 are side, cross-sectional views of the example wing assembly2600 of FIGS. 26-27. In the illustrated example, the track 2614 a iscurved and has a first curvature similar or identical to a secondcurvature of the third upper surface 2612 of the flap 2610. In otherexamples, the first curvature is different than the second curvature.For example, the track 2614 a may have a curvature similar or identicalto the example track 2504 of FIG. 25. In the illustrated example, whenthe flap 2610 is in the stowed position, a first portion of the track2614 a extends through of the slot 2700 (e.g., the first portion is notcovered by the trailing edge 2606), and a second portion of the track2614 a is covered by the trailing edge 2606. The example roller assembly2702 of FIG. 28 is disposed adjacent an aft end 2800 of the track 2614a. When the flap 2610 moves toward a deployed position, the track 2614 aapplies a force to the roller assembly 2702 and guides or directs theroller assembly 2702 downward in the orientation of FIGS. 28-29. As aresult, the example trailing edge 2606 elastically deforms (e.g., bends)from a first shape to a second shape. The example roller assembly 2702is disposed adjacent a fore end 2802 of the track 2614 a when theexample flap 2610 is in the deployed position. When the example flap2610 moves from the deployed position to the stowed position, the track2614 a applies a force to the roller assembly 2702 and guides the rollerassembly 2702 upward in the orientation of FIGS. 28-29. As a result, theexample trailing edge 2606 elastically deforms from the second shape tothe first shape.

FIG. 30 is a cross-sectional view of the example roller assembly 2702along line A-A of FIG. 29. In the illustrated example, the first roller2704 includes a first bracket 3000, a first wheel 3002 and a first axle3004. The example first axle 3004 rotatably couples the first wheel 3002to the first bracket 3000. The first axle 3004 may be a fastener (e.g.,a rivet), a pin, a shaft, a bearing and/or any other axle. In someexamples, the first wheel 3002 is in contact with the third uppersurface 2612 of the flap 2610 and/or a first flange 3006 of the track2614 a.

The example second roller 2706 includes a second bracket 3008, a secondwheel 3010 and a second axle 3012. The example second axle 3012 may be afastener, a pin, a shaft, a bearing and/or any other axle. In someexamples, the second wheel 3010 is in contact with the third uppersurface 2612 of the flap and/or a second flange 3014 of the track 2614a. In some examples, the roller assembly 2702 includes other numbers ofwheels (e.g., 1, 3, 4, 5, etc.). Additionally or alternatively, othertypes of roller assemblies and/or sliders are employed.

In the illustrated example, the track 2614 a is coupled to the thirdupper surface 2612 (e.g., a skin) of the flap 2610. In other examples,the track 2614 a is coupled to other portions of the flap 2610. Forexample, the track 2614 a may extend through a slot or aperture of thethird upper surface 2612 to be coupled to a rib and/or a rib cap of theflap 2610. In some examples, the track 2614 a includes a third flangeand a fourth flange opposite the first flange 3006 and the second flange3008, respectively. For example, the track 2614 a may have an I-shapedcross-sectional shape. The third flange and/or the fourth flange may becoupled to the third upper surface 2612 and/or any other portion of theflap 2610.

Although certain example methods, apparatus and articles of manufacturehave been disclosed herein, the scope of coverage of this patent is notlimited thereto. On the contrary, this patent covers all methods,apparatus and articles of manufacture fairly falling within the scope ofthe claims of this patent.

What is claimed is:
 1. An apparatus, comprising: a trailing edge of awing of an aircraft, the trailing edge having an elastically deformableskin defining a first surface, the trailing edge having a first end tobe fixed to the wing and a second end opposite the first end that is tomove relative to the first end; and a flap movably coupled to the secondend of the trailing edge, the flap movable between a stowed position anda deployed position, the trailing edge to elastically elongate when theflap moves from the stowed position to the deployed position and thetrailing edge is to elastically collapse when the flap moves from thedeployed position to the stowed position.
 2. The apparatus of claim 1,wherein the flap defines a second surface, the first surface and thesecond surface form a substantially continuous surface when the flap isin the stowed position and when the flap is in the deployed position. 3.The apparatus of claim 1, wherein the trailing edge is fixedly coupledto a spar of the wing.
 4. The apparatus of claim 1, wherein a firstportion of the skin has a first thickness and a second portion of theskin has a second thickness different than the first thickness.
 5. Theapparatus of claim 1, wherein the flap is movable to a third position toprovide a gap between the trailing edge and the flap.
 6. The apparatusof claim 1, wherein the trailing edge includes a flexible rib coupled tothe skin.
 7. The apparatus of claim 6, wherein the trailing edgeincludes a stringer coupled to the skin and the rib.
 8. The apparatus ofclaim 1, wherein the flap is an upper surface blown flap.
 9. Theapparatus of claim 1, wherein a first slope of the first surface and asecond slope of the second surface are substantially similar at ajuncture of the first surface and the second surface.
 10. An apparatuscomprising: a trailing edge of a wing of an aircraft, the trailing edgehaving a first end fixed to the wing and a second end opposite the firstend, the trailing edge having a flexible upper surface and a flexiblelower surface, the flexible upper surface and the flexible lower surfacebeing elastically deformable to enable the second end to bend relativeto the first end while the first end is fixed to the wing; and a flapmovably coupled to the second end of the trailing edge, the flap tocause the flexible upper surface and the flexible lower surface of thetrailing edge to elastically deform between a first shape and a secondshape different from the first shape when the flap moves between a firstposition and a second position relative to the trailing edge.
 11. Theapparatus of claim 10, wherein the flap and the trailing edge provide asubstantially continuous upper blown surface when the flap moves betweenthe first position and the second position.
 12. The apparatus of claim10, wherein the flap is to rotate relative to the trailing edge about anaxis of rotation.
 13. The apparatus of claim 12, further including afirst link to pivotally couple the flap to a hinge defining the axis ofrotation and a second link to pivotally couple the flap to the hinge.14. The apparatus of claim 13, further including an actuator operativelycoupled to at least one of the first link or the second link to move theflap between the first position and the second position.
 15. Theapparatus of claim 10, wherein the first end of the trailing edge is todirectly attach to a spar of the wing without a hinge, the first end ofthe trailing edge to remain in engagement with the spar of the wing whenthe flap moves between the first position and the second position. 16.An apparatus, comprising: a trailing edge of a wing of an aircraft, thetrailing edge having an elastically deformable skin, the trailing edgeincludes a first end fixed to the wing and a second end opposite thefirst end to move relative to the first end, the skin to elasticallydeform when the second end of the trailing edge moves relative to thefirst end of the trailing edge; and a flap movably coupled to thetrailing edge, the flap to apply a load to the trailing edge to causethe skin of the trailing edge to elastically deform between a firstposition and a second position when the flap moves between a stowedposition and a deployed position.
 17. The apparatus of claim 16, whereinat least one of the trailing edge or the flap includes a guide toprovide a motion path of the flap relative to the trailing edge.
 18. Theapparatus of claim 17, wherein the guide has a curvature that issubstantially similar to a curvature of an upper surface of the flap.19. The apparatus of claim 16, wherein a leading edge of the skin of thetrailing edge is to remain fixed to the wing when the flap moves betweenthe stowed position and the deployed position.
 20. The apparatus ofclaim 16, wherein the flap rotates relative to the trailing edge about apivot axis, the flap to apply a force to cause the trailing edge toelastically deform the skin when the flap rotates about the pivot.